Aeroplane stabilizer or control.



N TERRY.

AEROPLANE STABILIZER 0R CONTROL.

APPLICATION FILED MAR. 29. 1915- Patented Ed). 6, 1917.

Jil n/M701? w. 727mm r a WDOLG.

the object of which will construction and we snares rarri onion NERI rEaRY, or HARDISTY, ALBERTA, CANADA.

AEROPLANE STABILIZER 0R CONTROL.

To all whom it may concern:

Be it known that I, Nnnr TERRY, a subject of the King of Great Britain, and resident of Hardisty, in

M Specification of Letters Patent.

Application filed March 29, 1915.

Serial No. 17,879.

and lower planes :2 and 3 are spindles l1 and 12 carrying intermediate of their ends bell cranks 13 and 14, the horizontal arms of which are pivotally connected by means of the links 15 and 16 to the auxiliary planes 4 and 5, the vertical arms of the said bell being manually operated, to simplify the generally adapt the several parts to better tions required of them.

The invention consists essentially of the improved stabilizers particularly described and set forth in the following specification and accompanying drawings forming part of the same.

In the drawings, Figure 1 is a perspective view of an aeroplane embodying the present invention. Fig. 2 is a. front elevation of the pilot seat showing the control levers mounted thereon. Fig. the bolt adapted position. I

Like characters of reference refer to like parts in the several drawings.

Referring to the drawings, A represents an aeroplane of any usual construction comprising the ,fusilage 1 and the upper and lower planes 2 and 3, such aeroplane being provided with the usual prime mover and not forming part of the presept invention except in so far that the stabilizer B is mounted thereon it is deemed unnecessary to further describe the same.

to lock the seat in a fixed perform the several tune 3 is a perspective View of The stabilizer comprises auxiliary planes t and 5 pivota-lly mounted in front of their center of pressure to the upper plane 2 and adapted to be rotated in a vertical plane as the aeroplane is laterally tilted.

Pivotally supported from the upper plane 2 is the pilot seat 6 having the transversely extending rod 7 rigidly mounted on the bot tom thereof and carryin brackets 8 and 9,

be made clear hereafter.

Pivotally mounted intermediate of the standards 10 extending between the upper into anormal hoi'izontal posi Shcnidthe macl tiltin a long-git a? direction cranks being links 17 and pivotally mounted on the rod 7 and provided with spring controlled detents adapted to engage with the brackets 8 and 9.

The tail mounted in front of the to the fusilage 1 and is adapted to be rotated in a vertical plane, to which end it is proconnected by means of the Patented Feb. 6, 1911?.

18 to the levers 19 and 20 I 21 of the aeroplane is pivotally center of pressure vided with an eye bolt 22 connected to one end of the link 23, the opposite end of which is attached to the lever 24 pivotally mounted to the chair and provided with a spring con trolled detent adapted to engage with the quadrant 28 thereby permitting of the tail being fixed in any desired position relating to the pilots seat and be manually operated if desired.

Located below the chair is a spring controlled locking bolt 25 mounted in any con-,

venient manner to the fusilage 1 and adapted to be depressed by the foot of the pilot to which end the lever 26 is provided, pivotally mounted at one end to the fusilage, the other end carrying a pin adapted to engage with the said locking bolt, which when depressed is secured in position by the catch member 27.

It will be clea iqthat in the operation of the device should the aeroplane become, tilted the pilots seat 6 will swing about its upper pivoted end, the motion being trans mitted through the linksl'? and 18 to the bell cranks 13 and 14 which in turn through the links 15 and 16 rotate the auxiliary planes 4 and 5 ing the lifting of the machine and reducing the lift power on the elevated side of the mac thereby tending tb-bring the inachinebaeln will. again swing about .its upper pivoted point, the motion being transmitted to the tail 21 through the 23 thereby increasing or decreasing the lifting power and tending to bring the machine to a normal horizontal position.

When the pilots' seat 6 is fixed relatively to the :tusilage i by means of the locking bolt in a vertical plane so inereas power on the depressedside medium of the link 2 Ida-9 .matically assume a normal horizontal position when tilted either transversely or longi' tudinally.

As many changes could be made in the above construction and many apparently widely different embodiments of my invention, within the scope of the claim, constructed without departing from the spirit or scope thereof it is intended that all matter contained in the accompanying specification and drawings shall be interpreted as illustrative and not in a limiting sense.

What I claim as my invention is:

In an aeroplane, pivotally-mounted auxiliary planes, a pivotally mounted seat, means connecting the seat and auxiliary planes consisting of link and bell crank mechanism adapted to automatically actuate said-planes when the seat is oscillated, means for securing the seat in a rigid position and manually operating levers pivotally attached to the seat coactlhp,- with the link mechanism and adapted to actuate the auxiliary planes when the seat is rendered rigid.

In witness whereof I have hereunto set my hand in the presence of two witnesses.

NERI TERRY.

WVitnesses:

FRANK E. BUTALL, C. IAN BAZALGETTE. 

